Abstract : A digital control augmentation flight control computer utilizing distributed logic microcircuits and incremental computation has been fabricated and tested. The mechanization includes a sixth order control loop network and a complete self-adaptive identification system for the pitch axis of an aerodynamic vehicle. It has been shown to provide an adequate range of speed and resolution for use in this application and accurately model the analytic design. Investigations into the feasibility of formulating simple mechanized coarse identification systems which could be used with discrete gain changing have shown that they do not appreciably reduce mechanization requirements over more accurate continuous systems. (Author)